ZA200603229B - Rocket engine having guide vanes inthe nozzle of the engine - Google Patents
Rocket engine having guide vanes inthe nozzle of the engine Download PDFInfo
- Publication number
- ZA200603229B ZA200603229B ZA2006/03229A ZA200603229A ZA200603229B ZA 200603229 B ZA200603229 B ZA 200603229B ZA 2006/03229 A ZA2006/03229 A ZA 2006/03229A ZA 200603229 A ZA200603229 A ZA 200603229A ZA 200603229 B ZA200603229 B ZA 200603229B
- Authority
- ZA
- South Africa
- Prior art keywords
- vanes
- engine
- guide vanes
- nozzle
- fixed
- Prior art date
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract description 9
- 239000007789 gas Substances 0.000 description 20
- 230000001133 acceleration Effects 0.000 description 3
- 235000015842 Hesperis Nutrition 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- 239000000446 fuel Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/88—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using auxiliary rocket nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/84—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using movable nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/66—Steering by varying intensity or direction of thrust
- F42B10/663—Steering by varying intensity or direction of thrust using a plurality of transversally acting auxiliary nozzles, which are opened or closed by valves
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Toys (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Testing Of Engines (AREA)
Abstract
A rocket engine having guide vanes in the engine nozzle the guide vanes (2) being mounted for turning at or near the rearmost ends of fixed vanes (1) being parallel to the axis of the nozzle and protruding into the combustion chamber of the engine. The foremost ends (4) of the guide vanes (2) may be shielded by the rearmost ends of the fixed vanes (1), and the guide vanes (2) may be individually turnable.
Description
The present invention relates to a rocket engine having guide vanes in the engine nozzle.
Such guide vanes are used for guiding the rocket in a desired trajectory, by deflecting the flow of gas out of the engine in a particular direction.
In rockets gases are produced by combustion, of solid or liquid fuels, and the gases are accelerated through a nozzle and out through the rearmost end of the rocket. The
E acceleration of the gases causes a thrust against the rocket oppositely of the direction of acceleration.
Known guide vanes are situated in the supersonic part of the nozzle, i.e. behind the combustion chamber, and are journalled for turning at or near their middle. When such a vane is turned, the parts of the vane forwardly and rearwardly of the axis of turning protrude to the respective sides of a diametrical middie plane in the nozzle and are hit by accelerating gases having a high velocity. Thereby, parts of the gas flow are retarded, and large flow losses and a reduction of the effective thrust occur.
The aim of the present invention is to reduce or mainly to eliminate such flow losses by regulating of guide vanes in rockets. :
This is achieved by a rocket engine as defined in the succeeding, independent claim.
Hence, in the rocket engine according to the invention the guide vanes are journalled for turning at or near the rear end of fixed vanes which are parallel to the axis of the nozzle and protrude into the combustion chamber. In the combustion chamber the gases have approximately no velocity (relatively to the rocket) until they are heated by the combustion and are accelerated rearwardly through the nozzle. The largest acceleration takes place in the narrowest portion of the nozzle. The foremost end of the fixed vanes is situated in front of this portion, and is, therefore, not hit by gases having a high velocity, and the flow loss will here be at a minimum. Moreover, the foremost end of the guide vanes are shielded by the fixed vanes on which they are journalled, and are not hit by the flowing gases either. The accelerating and gradually rapidly flowing gases sweep along the sides of the fixed vanes and the guide vanes. When the guide vanes are turned, the gases are deflected and cause a thrust somewhat inclined relatively to the axis of the nozzle, and the direction of the rocket is changed.
The guide vanes may be individually steerable. Steering may take place by use of an electrical or mechanical system, for instance that a hinge between the fixed vane and the guide vane is associated with means for turning or that a shaft holding the guide vane can be turned.
The guide vanes must not necessarily have their axes of turning near the fixed vanes.
Having the axes of turning near the fixed vanes eliminates the impact of the flowing ~ gases against the guide vanes, but the energy requirement of the turning becomes relatively large. Having the axes of turning in a certain distance from the fixed vanes reduces the energy requirement of turning the guide vanes, but a certain impact of the gases against the guide vanes occurs. The axes of turning may in the principle be situated anywhere along the guide vanes.
The invention will in the following be explained by means of examples shown in the accompanying drawing.
Fig. 1 shows schematically a stationary vane protruding through a choke portion in a rocket nozzle and a guide vane hinged to the fixed vane or fastened to a tunable shaft.
Fig. 2 shows the fixed vane and the guide vane inclined relatively to the fixed vane, in order to cause a change of direction of the rocket by deflecting the flowing gases.
Fig. 3 shows an embodiment of the rear portion of a rocket nozzle, in which are mounted four fixed vanes, each equipped with a guide vane, the fixed vanes being mounted on a central cone in the nozzle. : Fig. 1 shows a fixed vane 1, having a rounded foremost end 3. Behind the fixed vane is a guide vane 2, having a rounded foremost end 4. The guide vane 2 is hinged to the fixed vane 1 or fastened to a not shown, turnable shaft. The fixed vane 1 protrudes through the choke portion 5 in the nozzle, i.e. the narrowest portion. The portion to the left of the choke portion 5 is the combustion chamber of the engine.
Fig. 2 shows the fixed vane 1 and the guide vane 2 turned relatively to the fixed vane 1.
The flowing gases sweep along the sides of the two vanes and are deflected by the 3s guide vane 2. Thereby, low pressures arise in the portions 6. The inlet loss against the guide vane is minimized, as the inlet of the gases towards the guide vane is on the lee side of the fixed vane.
Because the velocity of the gases in the combustion chamber, where the foremost ends 3 of the fixed vanes 1 are situated, is low, the gases do not hit these ends, but start accelerating rearwardly. Thereby, no fiow loss due to the ends 3 of the fixed vanes occurs. The gases sweep along the sides of the vanes 1 and 2, and because the foremost ends of the guide vanes 2 are shielded by the rearmost ends of the fixed oo vanes, the gases do not impact against the foremost ends of the guide vanes 2 either.
Fig. 3 shows how the vanes may be provided inside of a nozzle 7 in a rocket engine.
The example shows four pairs of vanes, without this constituting any limitation. The fixed vanes 1 are mounted on a central cone 8 in the nozzle, and connect the cone 8 and the nozzle 7. The guide vanes 2 are hinged to the rearmost end of the fixed vane 1 or 45 fastened to not shown, turnable shafts, and are in the fig. shown turned relatively to the vanes 1. :
The guide vanes 2 may be individually turnable.
Claims (3)
1. A rocket engine having guide vanes in the engine nozzle, characterized in that the guide vanes (2) are mounted for turning at or near the rearmost ends of fixed
5 . vanes (1) being parallel to the axis of the nozzle and protruding into the combustion chamber of the engine.
-
2. A rocket engine as claimed in claim 1, in which the foremost ends (4) of the guide vanes (2) mainly are shielded by the rearmost ends of the fixed vanes (1).
3. A rocket engine as claimed in claim 1 or 2, in which the guide vanes (2) are individually turnable.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| NO20034266A NO318772B1 (en) | 2003-09-24 | 2003-09-24 | Rocket engine with control wings in the engine nozzle |
| PCT/NO2004/000272 WO2005028844A1 (en) | 2003-09-24 | 2004-09-14 | Rocket engine having guide vanes in the nozzle of the engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| ZA200603229B true ZA200603229B (en) | 2007-07-25 |
Family
ID=29417547
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| ZA2006/03229A ZA200603229B (en) | 2003-09-24 | 2006-04-21 | Rocket engine having guide vanes inthe nozzle of the engine |
Country Status (11)
| Country | Link |
|---|---|
| US (1) | US7478778B2 (en) |
| EP (1) | EP1671025B1 (en) |
| JP (1) | JP4717818B2 (en) |
| AT (1) | ATE389106T1 (en) |
| AU (1) | AU2004274828B2 (en) |
| CA (1) | CA2539835C (en) |
| DE (1) | DE602004012428T2 (en) |
| IL (1) | IL174395A (en) |
| NO (1) | NO318772B1 (en) |
| WO (1) | WO2005028844A1 (en) |
| ZA (1) | ZA200603229B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008022289B4 (en) | 2008-04-25 | 2010-07-29 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | missile |
| DE102009013150B4 (en) | 2009-03-06 | 2011-05-05 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Component for use in hot gas flows |
| FR2995941B1 (en) * | 2012-09-21 | 2018-08-31 | Roxel France | DIVERGENT WITH JET DEVIATORS FOR SOLID CHARGING PROPELLERS |
| US11352978B2 (en) | 2020-06-24 | 2022-06-07 | Raytheon Company | Deflectable distributed aerospike rocket nozzle |
| CN112937916B (en) * | 2021-01-27 | 2022-12-06 | 西北工业大学深圳研究院 | Space robot for reducing influence of tail flow of attitude engine and working method thereof |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2510570A (en) * | 1946-03-26 | 1950-06-06 | Esther C Goddard | Rotatable discharge nozzle for fixed combustion chambers |
| US3260205A (en) * | 1964-09-28 | 1966-07-12 | Aerojet General Co | Fin actuated spin vane control device and method |
| US3743184A (en) * | 1972-07-07 | 1973-07-03 | Us Navy | Cylindrical throat nozzle with movable sonic blades for obtaining dual area throat and thrust vector control |
| US4063685A (en) * | 1976-07-30 | 1977-12-20 | The United States Of America As Represented By The Secretary Of The Army | Thrust vector control by circulation control over aerodynamic surfaces in a supersonic nozzle |
| US4131246A (en) * | 1977-02-04 | 1978-12-26 | Textron Inc. | Thrust vector control actuation system |
| US4175385A (en) | 1977-12-12 | 1979-11-27 | General Electric Company | Thrust reverser for an asymmetric aircraft exhaust nozzle |
| NZ198917A (en) | 1980-11-14 | 1985-01-31 | Commw Of Australia | Rocket controlled by spoiler tabs in exhaust |
| US4627586A (en) * | 1984-10-29 | 1986-12-09 | The United States Of America As Represented By The Secretary Of The Navy | Thrust vectoring apparatus for maneuvering missile in flight |
| US5078336A (en) * | 1989-07-21 | 1992-01-07 | Carter Gregory E | Spin-stabilized missile with plug nozzle |
| US5511745A (en) | 1994-12-30 | 1996-04-30 | Thiokol Corporation | Vectorable nozzle having jet vanes |
| US5806791A (en) | 1995-05-26 | 1998-09-15 | Raytheon Company | Missile jet vane control system and method |
| JP4286388B2 (en) * | 1999-07-02 | 2009-06-24 | ダイセル化学工業株式会社 | rocket |
| US6450443B1 (en) * | 2000-08-17 | 2002-09-17 | The United States Of America As Represented By The Secretary Of The Navy | High torque 2.75-inch rocket nozzle |
| JP2002227723A (en) * | 2001-02-02 | 2002-08-14 | Ihi Aerospace Co Ltd | Thrust control type solid rocket motor |
-
2003
- 2003-09-24 NO NO20034266A patent/NO318772B1/en not_active IP Right Cessation
-
2004
- 2004-09-14 DE DE602004012428T patent/DE602004012428T2/en active Active
- 2004-09-14 WO PCT/NO2004/000272 patent/WO2005028844A1/en active Application Filing
- 2004-09-14 EP EP04775056A patent/EP1671025B1/en active Active
- 2004-09-14 AU AU2004274828A patent/AU2004274828B2/en active Active
- 2004-09-14 CA CA002539835A patent/CA2539835C/en active Active
- 2004-09-14 AT AT04775056T patent/ATE389106T1/en not_active IP Right Cessation
- 2004-09-14 US US10/572,862 patent/US7478778B2/en active Active
- 2004-09-14 JP JP2006527932A patent/JP4717818B2/en active Active
-
2006
- 2006-03-19 IL IL174395A patent/IL174395A/en active IP Right Grant
- 2006-04-21 ZA ZA2006/03229A patent/ZA200603229B/en unknown
Also Published As
| Publication number | Publication date |
|---|---|
| US7478778B2 (en) | 2009-01-20 |
| NO318772B1 (en) | 2005-05-02 |
| CA2539835C (en) | 2009-09-01 |
| EP1671025A1 (en) | 2006-06-21 |
| DE602004012428T2 (en) | 2009-03-19 |
| DE602004012428D1 (en) | 2008-04-24 |
| AU2004274828A1 (en) | 2005-03-31 |
| WO2005028844A1 (en) | 2005-03-31 |
| IL174395A (en) | 2010-12-30 |
| IL174395A0 (en) | 2006-08-01 |
| JP2007506905A (en) | 2007-03-22 |
| CA2539835A1 (en) | 2005-03-31 |
| JP4717818B2 (en) | 2011-07-06 |
| US20070152096A1 (en) | 2007-07-05 |
| AU2004274828B2 (en) | 2010-11-11 |
| NO20034266D0 (en) | 2003-09-24 |
| EP1671025B1 (en) | 2008-03-12 |
| ATE389106T1 (en) | 2008-03-15 |
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